48results about How to "Improve flight characteristics" patented technology

Ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams.

Disclosed is a placement system for a free-flying kite-type wind-attacked element (101) in a watercraft in which the kite-type wind-attacked element (101) comprising a profiled wing is connected to the vessel body via a traction rope (1.1). Said wind-attacked element (101) can be guided from a neutral position on board the watercraft into a raised position that is free from obstacles located at the same or a higher level. An azimuthally pivotable fixture (181) is provided by means of which the wind-attacked element (101) can be brought into a position in which the same is exposed to an sufficient wind effect. Furthermore, a docking receiving device (181) is provided which is to be removably connected to the docking adapter of the wind-attacked element (101) on the side facing away from the wind while also allowing the wind-attacked element to be furled with the aid of automatically engaging holding means.

A ring airfoil projectile is defined by an annular body which defines a central passage. The body is constructed so that a center of pressure is substantially coincident with a center of gravity thereof. The body is preferably constructed of a nose section and tail section, the nose section of a material having a higher density than the material forming the tail section. The ring airfoil projectile is configured to deliver a payload to a target. Cavities extend inwardly from the outer surface of the airfoil, preferably in the nose section. The cavities accept payload or a strip containing payload. The ring airfoil projectile is configured to travel with minimum path dispersion, and to deliver the payload upon impacting a target.

A rotorcraft that utilizes both a main compound rotor and a plurality of tiltrotors is disclosed. The main rotor and the thrusters can provide vertical lift for vertical take-off and landing of the rotorcraft. The thrusters of the rotorcraft can articulate to a horizontal position to facilitate horizontal flight. The main rotor of the rotorcraft can continue to provide vertical lift for the rotorcraft in horizontal flight, as well as operate in an autorotation mode. In the event of a failure of the main power source of the rotorcraft, the main rotor in autorotation mode can safety land the rotorcraft. In the autorotation mode, the main rotor can create electrical energy that is stored in a battery and can be used to power the plurality of thrusters. The rotorcraft can also be configured in an anti-torque mode, where the thrusters cancel out the torque of the main rotor.

A magnetic recording medium is provided, which has a recording layer formed in a concavo-convex pattern and makes it possible to obtain the stable flying characteristics of a head. In the magnetic recording medium, concave portions between recording elements are filled with a non-magnetic material. Thus, the surface of the magnetic recording medium takes a concavo-convex shape which is different from the concavo-convex pattern of the recording layer. Also, the arithmetical mean deviation of the assessed profile of the concavo-convex shape in the surface is restricted to 1 nm or less.

A load hook substructure for attachment onto or into the cabin structure of a helicopter, having a housing in which a shaft with a hook attachment is mounted, such that a load hook can be connected with the shaft and thereby with the load hook substructure; this improves the flying characteristics of the helicopter in the case of flights with a load carried underneath. This is achieved in that the shaft passes through the interior of the housing in the longitudinal direction between a housing end wall and a housing wall, such that it can move linearly, and a return spring device is arranged between a damping plate arranged on the shaft and the housing end wall, and a damping device is arranged between the damping plate and the lower housing wall. The damping device has at least one flexibly compressible damping element, which develops a damping action in the event of a linear movement of the shaft.

A kite has a cover sheet having first and second opposed main surfaces. A frame assembly is attached to the second main surface of the cover sheet to define a body having an overall height and an overall width. The frame assembly has frame members connected together to form a generally conical-shaped sector portion defining an air passage through which air flows when the kite is in flight. A rotational vane is mounted on the frame assembly for undergoing rotation to regulate the flow of air flowing through the air passage when the kite is in flight.

A toy projectile that has two parts, a cup shaped inner core having a top wall, an annular wall extending from the top wall to a bead adjacent to a bottom end, and an outer covering being somewhat donut shaped with a central opening, a top end, a bottom end, a lower recess, a curved exterior surface and a chamfer adjacent to the bottom end. The inner core is received in the central opening of the outer covering such that the top wall of the inner core is continuous with the top end of the outer covering. The bottom of the projectile may be open or covered. The projectile includes geometric aspect ratios that provide the projectile with excellent flight characteristics. The ratios are: projectile outer diameter to projectile height between 4:1 to 5.2:1; projectile outer diameter to core outer diameter between 1.20:1 to 1.45 to 1; projectile height to core bead height between 2.3:1 to 3.25:1; outer covering volume to inner core volume between 2.4:1 to 5.8:1; profile radius to projectile height between 0.5:1 to 0.8:1; and chamfer height to chamfer width between 2:1 to 6.1.

An aircraft has a propulsion unit and a fuselage unit. The propulsion unit has a first rotor for providing a propulsion force on the aircraft. The fuselage unit extends along a rotation axis of the first rotor and has a rotationally symmetrical shape with respect to the rotation axis of the first rotor. The fuselage unit has a suspension at a first end by which the fuselage unit is coupled to the first rotor so that the fuselage unit is spaced apart from the first rotor along the rotation axis. A detection unit for the detection of environmental information is provided in the area of a second end of the fuselage unit. The propulsion unit is designed to keep the aircraft in a hovering flight condition so that a relative position of the aircraft with respect to a reference point on the Earth's surface remains unchanged.

The present invention relates to an aerial fire-fighting bucket. The bucket includes a base plate and a valve arrangement including at least one valve and a liner actuator. The base plate includes at least one aperture and the valve is arranged to block the aperture in a closed position and to allow fluid to pass from within the bucket through the aperture when in an open position. The valve is arranged to be moved by the linear actuator generally transversely across an upper face of the base plate between the closed position and the open position of the valve to progressively reveal the aperture.

The purpose of the invention is to provide a magnetic recording medium in which the surface roughness of the magnetic recording layer can be reduced without deterioration of the magnetic properties of the magnetic recording layer. The magnetic recording medium of the present invention includes a substrate, a seed layer on the substrate, and a magnetic recording layer on the seed layer, wherein the seed layer contains Mn, Cr, and O, and has a spinel structure.

The archery arrow having improved flight characteristics of the present invention is designed to improve the accuracy of the arrow which is equipped with a dampening medium within the central bore of the arrow shaft. The dampening materials in an embodiment may include, but not be limited to, silicon, epoxies or urethanes and selection of various dampening materials may provide for varying degrees of stiffness. The dampening effects of internal dampening materials decrease the initial deflection distance of the arrow and also serves to decrease the deflection with each oscillation. In addition, the dampening medium adopted in the present invention provides for an arrow having a selectable center of gravity location that has improved flight characteristics. Thus, the dampening materials adopted in the present invention provide for a selected location of center of gravity and a desired attenuation of oscillations.